| 高温燃气流风洞全尺寸舱段热结构试验技术研究 |
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| 引用本文： | 赵玲,李文浩,岳晖,田宁,邹样辉. 高温燃气流风洞全尺寸舱段热结构试验技术研究[J]. 气体物理, 2021, 6(5): 44-50. DOI: 10.19527/j.cnki.2096-1642.0889 |
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| 作者姓名： | 赵玲 李文浩 岳晖 田宁 邹样辉 |
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| 作者单位： | 北京航天长征飞行器研究所,北京100076 |
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| 摘 要： | 利用200 MW高温燃气流风洞,开展1:1全尺寸舱段模型热结构/热匹配试验.围绕风洞试验状态调节、介质影响热流设计评估、多台阶长时间热流校测等技术问题,开展高温燃气流风洞舱段类模型试验设计方法研究.引入新的燃气流风洞试验状态调节方法和考虑燃气介质差异的等效冷壁热流修正方法,并通过长时间变工况表面热流测试方法的建立,实现...
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| 关 键 词： | 高温燃气流风洞 热结构 热匹配 全尺寸 热流修正 |
| 收稿时间： | 2020-12-01 |
Thermal Structure Test of Full-Scale Cabin Component in 200 MW High Temperature Tunnel |
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| Affiliation: | Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
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| Abstract: | A thermal structure and thermal match test of a full-scale cabin component was conducted in a 200 MW high temperature combustion-heated tunnel. New test methods were developed for some key techniques like tunnel state adjustment, effect of test medium and long term heat flow measurement. New methods of combustion-heated tunnel operation design and equivalent cold-wall heat-flux correction considering combustion gas effects were applied. Long term heat flow evaluation method was also used to simulated variable heat flux boundary conditions at the same test trajectory. The technology method was applied to a full-scale cabin component test successfully. The experiment results show that the aero-heating environments were exactly simulated and the technique was effective and feasible. |
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